GB1358076A - Oil manifolds and coolers for ducted fan gas turbine engines - Google Patents

Oil manifolds and coolers for ducted fan gas turbine engines

Info

Publication number
GB1358076A
GB1358076A GB2889271A GB2889271A GB1358076A GB 1358076 A GB1358076 A GB 1358076A GB 2889271 A GB2889271 A GB 2889271A GB 2889271 A GB2889271 A GB 2889271A GB 1358076 A GB1358076 A GB 1358076A
Authority
GB
United Kingdom
Prior art keywords
oil
tank
manifolds
ducted fan
gas turbine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
GB2889271A
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB2889271A priority Critical patent/GB1358076A/en
Publication of GB1358076A publication Critical patent/GB1358076A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1358076 Gas turbine ducted fan engines ROLLS-ROYCE (1971) Ltd 19 June 1972 [19 June 1971] 28892/71 Heading F1J The invention relates to a gas turbine ducted fan engine and to an arrangement of annular or part-annular oil manifolds and oil cooler elements. The engine shown comprises a core engine 1 which is arranged to drive a ducted fan 2, the core engine comprising an outer casing 5 within which is mounted an annular oil tank 7, the tank being associated with a plurality of oil cooler elements 10 which project radially into the fan duct. The tank 7 is associated with a pair of manifolds 14, 15 and the manifolds are inter-connected by the plurality of oil cooler elements 10, each element being in the form of a hollow vane in which is disposed an inner member 17 so as to form a narrow oil flow passage; the vane is provided with cooling fins 30. Hot oil and air passes into the manifold 14 and discharges through opening 12 into the hollow vane 10 where it is cooled by the fan air flow. The oil and air discharges from the vane through opening 13 into the manifold 15 and thence through a spray bar 16 from which the oil and air mixture is discharged on to an arcuate plate 20 which is formed with radially outwardly plunged holes 21. The oil passes across the plate and is collected in the tank while the air passes through the holes 21 and is vented to atmosphere. The cooled oil is re-circulated.
GB2889271A 1971-06-19 1971-06-19 Oil manifolds and coolers for ducted fan gas turbine engines Expired GB1358076A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB2889271A GB1358076A (en) 1971-06-19 1971-06-19 Oil manifolds and coolers for ducted fan gas turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2889271A GB1358076A (en) 1971-06-19 1971-06-19 Oil manifolds and coolers for ducted fan gas turbine engines

Publications (1)

Publication Number Publication Date
GB1358076A true GB1358076A (en) 1974-06-26

Family

ID=10282877

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2889271A Expired GB1358076A (en) 1971-06-19 1971-06-19 Oil manifolds and coolers for ducted fan gas turbine engines

Country Status (1)

Country Link
GB (1) GB1358076A (en)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2152147A (en) * 1983-12-27 1985-07-31 Gen Electric Gas turbine engine component cooling system
US4601202A (en) * 1983-12-27 1986-07-22 General Electric Company Gas turbine engine component cooling system
WO2005005810A1 (en) * 2003-07-08 2005-01-20 Rolls-Royce Plc Aircraft turbine engine arrangement
EP1630358A2 (en) 2004-08-26 2006-03-01 United Technologies Corporation A gas turbine engine frame with an integral fluid reservoir and air/fluid heat exchanger
WO2014143210A1 (en) * 2013-03-14 2014-09-18 Rolls-Royce North American Technologies, Inc. Gas turbine engine flow duct having two rows of integrated heat exchangers
WO2014151685A1 (en) 2013-03-15 2014-09-25 United Technologies Corporation Gas turbine engine with air-oil cooler oil tank
EP2847448B1 (en) 2012-05-07 2016-12-21 United Technologies Corporation Gas turbine engine oil tank
EP3165719A1 (en) * 2015-10-30 2017-05-10 General Electric Company Gas turbine engine sump heat exchanger
FR3059353A1 (en) * 2016-11-29 2018-06-01 Safran Aircraft Engines AIRBOARD TURBOMACHINE EXIT OUTPUT AUDE COMPRISING A LUBRICANT-BENDED ZONE HAVING AN IMPROVED DESIGN
WO2021121976A1 (en) * 2019-12-19 2021-06-24 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine engine of an aircraft having oil cooling
EP3981967A1 (en) * 2020-10-09 2022-04-13 Rolls-Royce plc Turbofan with air-cooled heat exchanger in the inlet flow upstream of the fan
US11702958B2 (en) 2021-09-23 2023-07-18 General Electric Company System and method of regulating thermal transport bus pressure
US11788470B2 (en) 2021-03-01 2023-10-17 General Electric Company Gas turbine engine thermal management

Cited By (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4601202A (en) * 1983-12-27 1986-07-22 General Electric Company Gas turbine engine component cooling system
US4608819A (en) * 1983-12-27 1986-09-02 General Electric Company Gas turbine engine component cooling system
GB2152147A (en) * 1983-12-27 1985-07-31 Gen Electric Gas turbine engine component cooling system
WO2005005810A1 (en) * 2003-07-08 2005-01-20 Rolls-Royce Plc Aircraft turbine engine arrangement
US7484354B2 (en) 2003-07-08 2009-02-03 Rolls-Royce Plc Aircraft engine arrangement
EP1630358A2 (en) 2004-08-26 2006-03-01 United Technologies Corporation A gas turbine engine frame with an integral fluid reservoir and air/fluid heat exchanger
EP1630358A3 (en) * 2004-08-26 2008-12-31 United Technologies Corporation A gas turbine engine frame with an integral fluid reservoir and air/fluid heat exchanger
EP2847448B1 (en) 2012-05-07 2016-12-21 United Technologies Corporation Gas turbine engine oil tank
US10808608B2 (en) 2012-05-07 2020-10-20 Raytheon Technologies Corporation Gas turbine engine oil tank
US10072569B2 (en) 2012-05-07 2018-09-11 United Technologies Corporation Gas turbine engine oil tank
US9790893B2 (en) 2013-03-14 2017-10-17 Rolls-Royce North American Technologies, Inc. Gas turbine engine flow duct having integrated heat exchanger
WO2014143210A1 (en) * 2013-03-14 2014-09-18 Rolls-Royce North American Technologies, Inc. Gas turbine engine flow duct having two rows of integrated heat exchangers
WO2014151685A1 (en) 2013-03-15 2014-09-25 United Technologies Corporation Gas turbine engine with air-oil cooler oil tank
EP2971672A4 (en) * 2013-03-15 2016-11-16 United Technologies Corp Gas turbine engine with air-oil cooler oil tank
US10352191B2 (en) 2013-03-15 2019-07-16 United Technologies Corporation Gas turbine engine with air-oil cooler oil tank
EP3428427A1 (en) * 2013-03-15 2019-01-16 United Technologies Corporation Gas turbine engine with air-oil cooler oil tank
EP3165719A1 (en) * 2015-10-30 2017-05-10 General Electric Company Gas turbine engine sump heat exchanger
US10100736B2 (en) 2015-10-30 2018-10-16 General Electric Company Gas turbine engine sump heat exchanger
RU2747652C2 (en) * 2016-11-29 2021-05-11 Сафран Эркрафт Энджинз Aircraft turbomachine outlet guide blade containing a curved lubricant channel of improved design
FR3059353A1 (en) * 2016-11-29 2018-06-01 Safran Aircraft Engines AIRBOARD TURBOMACHINE EXIT OUTPUT AUDE COMPRISING A LUBRICANT-BENDED ZONE HAVING AN IMPROVED DESIGN
WO2018100278A1 (en) * 2016-11-29 2018-06-07 Safran Aircraft Engines Aircraft turbomachine exit guide vane comprising a bent lubricant passage of improved design
US11125091B2 (en) 2016-11-29 2021-09-21 Safran Aircraft Engines Aircraft turbo machine exit guide vane comprising a bent lubricant passage of improved design
WO2021121976A1 (en) * 2019-12-19 2021-06-24 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine engine of an aircraft having oil cooling
EP3981967A1 (en) * 2020-10-09 2022-04-13 Rolls-Royce plc Turbofan with air-cooled heat exchanger in the inlet flow upstream of the fan
US11692484B2 (en) 2020-10-09 2023-07-04 Rolls-Royce Plc Turbofan engine with heat exchanger module having optimized fan to element area parameter
US11788470B2 (en) 2021-03-01 2023-10-17 General Electric Company Gas turbine engine thermal management
US11702958B2 (en) 2021-09-23 2023-07-18 General Electric Company System and method of regulating thermal transport bus pressure

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Legal Events

Date Code Title Description
PS Patent sealed
PLNP Patent lapsed through nonpayment of renewal fees